M. Saiprakash - Department of Aerospace Engineering MIT Campus, Anna University, Chennai-۶۰۰۰۴۴,India
C. SenthilKumar - Department of Aerospace Engineering MIT Campus, Anna University, Chennai-۶۰۰۰۴۴,India
G. K. Sunil - Directorate of Aerodynamics, Defence Research & Development Laboratory, Hyderabad -۵۰۰۰۵۸, India
S. P. Rampratap - Directorate of Aerodynamics, Defence Research & Development Laboratory, Hyderabad -۵۰۰۰۵۸, India
V. Shanmugam - Directorate of Aerodynamics, Defence Research & Development Laboratory, Hyderabad -۵۰۰۰۵۸, India
G. Balu - Directorate of Aerodynamics, Defence Research & Development Laboratory, Hyderabad -۵۰۰۰۵۸, India

The flow field around a Sharp cone model configuration has been investigated by means of Schlieren facility in hypersonic shock tunnel. The time dependent evolution of flow around a cone of angle ۱۱.۳۸° with base radius of ۱۵۰mm has been visualized for a flow Mach number M = ۶.۵. Experiments have been carried out with Helium as driver gas and air as test gas to visualize the hypersonic flow field. The flow establishment, steady state, and termination process of the hypersonic flow have been visualized for two different angles of attack, namely ۰°&۵°. Experimentally measured shock angle compares well with the theoretical and the computational study. The measured shock layer thickness compares well with the numerical simulation for both angles of attack.

Sharp Cone model, High speed Schlieren facility, Hypersonic shock, Tunnel, Shock layer thickness